US4680199A - Method for depositing a layer of abrasive material on a substrate - Google Patents

Method for depositing a layer of abrasive material on a substrate Download PDF

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Publication number
US4680199A
US4680199A US06/842,591 US84259186A US4680199A US 4680199 A US4680199 A US 4680199A US 84259186 A US84259186 A US 84259186A US 4680199 A US4680199 A US 4680199A
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United States
Prior art keywords
particles
article
blade
suction
layer
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Expired - Lifetime
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US06/842,591
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English (en)
Inventor
John H. Vontell
Roscoe A. Pike
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Raytheon Technologies Corp
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United Technologies Corp
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Assigned to UNITED TECHNOLOGIES CORPORATION, A CORP OF DELAWARE reassignment UNITED TECHNOLOGIES CORPORATION, A CORP OF DELAWARE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: PIKE, ROSCOE A., VONTELL, JOHN H.
Priority to US06/842,591 priority Critical patent/US4680199A/en
Priority to EP87630036A priority patent/EP0238434A3/en
Priority to AU70411/87A priority patent/AU585800B2/en
Priority to JP62067762A priority patent/JPS62246466A/ja
Priority to MX005642A priority patent/MX166013B/es
Priority to CA000532636A priority patent/CA1302798C/en
Priority to IL81948A priority patent/IL81948A/xx
Priority to KR1019870002588A priority patent/KR950006398B1/ko
Publication of US4680199A publication Critical patent/US4680199A/en
Application granted granted Critical
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Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment

Definitions

  • the present invention relates to a method for depositing particulate material on a substrate. More specifically, it relates to a method for depositing a surface layer containing spaced apart abrasive particulate on the tip surface of a turbine engine component.
  • Gas turbine engines and other turbomachines have rows of rotating blades contained within a generally cylindrical case. As the blades rotate, their tips move in close proximity to the case. To maximize engine operating efficiency, the leakage of the gas or other working fluid around the blade tips should be minimized. As has been known for some time, this may be achieved by blade and sealing systems in which the blade tips rub against a seal attached to the interior of the engine case. Generally, the blade tip is made to be harder and more abrasive than the seal; thus, the blade tips will cut into the seal during those portions of the engine operating cycle when they come into contact with each other.
  • abrasive particles which are randomly distributed in a matrix material
  • coated abrasives made from alumina, silica and silicon carbide are common products, as are metal bonded diamond and cubic boron nitride grinding tools.
  • Such tools are often made by electrodeposition techniques.
  • electrodeposition techniques In U.S. Pat. No. 4,227,703, such techniques are used to deposit an abrasive layer on a turbine blade tip.
  • the limited composition of electrodeposited matrix alloys limits the usefulness of this method.
  • Sprayed deposits containing metal and ceramic abrasives are also well known. See, e.g., commonly assigned U.S. Pat. No. 4,386,112.
  • an abrasive layer When an abrasive layer is provided on a superalloy turbine blade tip, its method of application must be metallurgically compatible with obtaining or maintaining the desired properties of the superalloy substrate. Since turbine blade alloys reflect a highly refined metallurgical art, there are limits on the techniques used with abrasive layer fabrication. Also, the abrasive layer is not a structural material and its weight imposes stresses on the blade substrate during use, i.e., when the blade rotates at high speed. Thus it is highly desirable that the minimum thickness abrasive layer be applied. Since blades are finished to length tolerances of 0.05 mm or less, this means that both the preparation of the substrate and the application of the abrasive layer must be carried out with high precision. All these considerations place severe restraints on the kinds of materials and processing techniques which are useful.
  • An object of the invention is a method for providing a single layer of spaced apart particles on the surface of an article. Another object of the invention is to deposit such particles in a high concentration and uniform distribution on a turbine blade tip. Yet another object of the invention is to provide an abrasive layer having high temperature operating capability on the tip surface of a turbine blade.
  • a method for depositing a single layer of particles in a desired pattern on the surface of an article comprises the steps of (a) drawing a vacuum through a transfer tool having a plurality of apertures arranged in said desired pattern, the size of each aperture being such that the vacuum holds only one particle in overlying relation to each aperture; (b) positioning the tool and the particles held thereto over the article surface; and (c) decreasing the vacuum level such that the particles fall onto the surface, their position on the surface substantially corresponding with the position of the apertures.
  • a layer of adhesive is present on the surface so that when the particles drop onto it, they are adhesively attached to the surface.
  • the particles have a metal cladding thereon, and the article is then heated to volatilize the adhesive and sinter bond the clad particles to the surface.
  • the invention is particularly useful in the fabrication of an abrasive layer on the tip surface of a rotor blade used in a gas turbine engine.
  • the particle density per unit area of blade tip surface must be maximized, while at the same time the interparticle contact must be minimized.
  • the particles must be securely bonded to the blade tip to withstand the stresses of engine operation.
  • a matrix alloy material is deposited on the surface so as to cover the particles and to fill in the spaces between the particles.
  • the particulate bearing matrix is then simultaneously heated and pressed to eliminate any voids in the matrix material and securely bond the matrix to the substrate and, by interdiffusion, to the cladding on each particle.
  • the abrasive layer is then machined to a relatively flat surface, and then part of the matrix is chemically removed to cause portions of the particles to project into space.
  • the abrasive particles are particularly sized with respect to the matrix layer thickness. Control over the particle sizing and aspect ratio are necessary to insure that a portion of most of the particles projects into space, while at the same time, all of the particles are securely bonded to the blade tip surface. Particles sized between Nos. 35-40 U.S. Sieve Series (0.42-0.50 mm nominal openings) are used when the matrix layer thickness is about 0.38 mm. Most preferably, the particles are uniformly spaced apart in a regular pattern on the blade tip surface. Depending on the expected interaction between the abrasive layer and the seal during engine operation, the particle density may be varied between about 35 to 110 particles per cm 2 . This relatively close spacing necessitates using particles with aspect ratios less than 1.9 to 1, so that less than about 15% of the particles will contact one another after they are bonded to the tip surface.
  • the abrasive layer produced according to the invention is economical in the use of materials and has good durability when interacting with ceramic seals.
  • FIG. 1 generally shows the radially outer portion of a typical gas turbine blade having an abrasive layer made according to the invention
  • FIG. 2 shows in side view the appearance of a prior art abrasive layer
  • FIG. 3 shows in side view the appearance of an abrasive layer produced according to the teachings of the present invention
  • FIGS. 4-7 show simplified, schematic views of the method by which abrasive particles are placed on the surface of a turbine blade tip according to the present invention
  • FIG. 8 shows a perspective view of FIG. 6
  • FIG. 9 shows in side view the appearance of the abrasive particles enveloped in a matrix material.
  • FIG. 10 shows the abrasive layer machined to a flat surface.
  • an abrasive layer 10 is formed on the tip surface 11 of the airfoil portion 12 of a gas turbine blade 14.
  • the blade 14 is preferably made of a nickel base superalloy (such as the single crystal alloy of U.S. Pat. No. 4,209,348), while the abrasive layer 10 is comprised of a nickel base superalloy matrix 16 and alumina coated silicon carbide particles 18.
  • nickel base superalloy such as the single crystal alloy of U.S. Pat. No. 4,209,3
  • other materials may be used in the practice of the invention.
  • the abrasive layer 10 is subjected to very high stresses during engine operation, and therefore it is important that the layer 10 have a certain configuration and properties to perform its function.
  • the particles 18 must be disposed on the tip surface 11 in a certain manner to obtain optimum performance.
  • abrasive layer 20 for a turbine blade 21 shown in FIG. 2 there are randomly disposed abrasive particles 22 within a matrix metal 24.
  • the abrasive layer 10 made according to the invention is characterized by a single layer of abrasive particles 18 surrounded by matrix material 16.
  • Use of a single layer of abrasives 18 minimizes the mass of the entire layer 10, thus reducing the centripetal force on the blade 14 as it rotates during engine operation.
  • the matrix metal 16 has a thickness W less than the overall thickness T of the particles 18.
  • a portion of each particle 18 projects into space, thereby enabling favorable rubbing interaction with metal or ceramic seals during engine operation.
  • the unexposed portion of the particles 18 must be surrounded by matrix metal 16, and the particles 18 must be closely spaced apart from each other.
  • the matrix metal 16 as well as particles 18 must be securely bonded to the blade tip 11.
  • at least about 80-90% of the particulate surface area (excluding that surface area exposed at the blade tip) is surrounded by matrix metal 16 rather than being in contact with another particle 18.
  • the particles 18 are, in general, evenly and densely spaced on the blade tip 11. Densities of about 35-110 particles per cm 2 of tip surface 11 are obtained with the invention method of application, with about 50 particulates per cm 2 being preferred.
  • the particles 18 have a thickness (length), T, and the matrix thickness W is about 50-90 percent of the particle thickness T.
  • Silicon carbide particles of No. 35-40 U.S. Sieve Series Size (nominally 0.42-0.50 mm) have been found useful in the practice of the invention; up to U.S. Pat. No. 20 (0.83 mm) size also appears useful.
  • FIGS. 4-8 show how the particulates 18 are laid on the blade tip surface 11 where they will be subsequently permanently adhered.
  • the silicon carbide particulates Prior to placing the silicon carbide particulates on the surface 11, they are first coated with about 0.010 mm of vapor deposited alumina according to the aforementioned Johnson et al patent, and then clad with a layer of metal, such as vapor or electrodeposited nickel, to a thickness of about 0.002-0.050 mm.
  • Procedures for applying nickel coatings to ceramic particulates are commercially available and also are revealed in U.S. Pat. Nos. 3,920,410, 4,291,089 and 4,374,173. If the ceramic particulate material is inherently resistant to reaction with the matrix material then the alumina coating is not necessary. (Neither the alumina coating nor metal cladding are shown in the Figures.)
  • a polymer adhesive 48 which is capable of being volatilized at less than about 540° C. is applied to the surface 11.
  • the purpose of the adhesive 48 is to hold the abrasive particles 18 in place after they are deposited on the blade tip 11.
  • a 1-20 volume percent polystyrene in toluene solution is preferred.
  • the particles 18 in the abrasive layer 10 should be densely arranged on the blade tip 11 in a uniformly spaced apart pattern.
  • a vacuum suction
  • the apertures are perforations 44 in a rigid plate 42. The size of each perforation 44 or aperture is such that when the plate 42 is brought near a source of the particles 18, the vacuum draws the particles 18 against the plate 42, and only one particle 18 is held over each aperture.
  • some particles 18 may be attracted to the plate 42 or to other particles 18 by, e.g., electrostatic forces, rather than held thereto by the vacuum. Such excess particles are dislodged from the plate 42 by gently tapping the plate 42, taking care not to dislodge the particles 18 held by the vacuum.
  • the perforations 44 are particularly dimensioned relative to the particle size. The diameter of each perforation 44 must be large enough such that the force of the vacuum is sufficient to draw the particles 18 against the plate 42. At the same time, the perforations 44 must be small enough to prevent the particles 18 from passing therethrough. Preferably, the diameter of each perforation 44 is about 3/4 of the particle size.
  • the area of the plate 42 covered by the particles 18 is slightly larger than the actual blade tip surface 11. This is accomplished by constructing the container 46, which holds the loosely lying particles, in the shape of an oversized blade tip; once the plate 42 is brought near the container and the vacuum turned on, the particles 18 will be attracted to the plate 42 in the pattern shown in FIG. 8.
  • the base 49 of the container 46 is a screen or mesh type material.
  • the plate 42 is positioned over the blade tip 11 so that the perforations 44 (and the particles 18 overlying them) are aligned with the desired position of the particles 18 on the blade tip 11, as shown in FIG. 8.
  • the tip 11 is coated with a layer 48 of adhesive.
  • the blade 14 is heated to volatilize the adhesive 48, which also causes solid state bonding (sintering) of the metal cladding to the tip surface 11.
  • the heat treatment is preferably carried out at about 1080° C. for 2 hours, in a vacuum or inert gas atmosphere. Use of such a protective atmosphere precludes oxidation of the cladding and blade tip 11.
  • the particles 18 are oversprayed with a layer of matrix material 16 deposited by plasma arc spraying to a thickness T' as shown in FIG. 9.
  • a nickel base superalloy of the type generally described in the aforementioned Johnson et al patent may be used.
  • the preferred matrix composition is, by weight percent, about 25 Cr, 8 W, 4 Ta, 6 Al, 1.0 Hf, 0.1 Y, 0.23 C, balance Ni.
  • the blade 14 is positioned with respect to the plasma arc device so that the tip cross section is generally perpendicular to the axis along which the molten matrix particles travel.
  • the blade 14 is suitably masked around its periphery so that errant spray does not deposit on the sides of the blade 14.
  • the matrix material 16 is applied to a thickness of about 0.6-1.3 mm, preferably 1.1-1.3 mm.
  • the sprayed layer of matrix material 16 will have about 95 percent theoretical density, it will nonetheless be characterized by some porosity or voids.
  • the voids are characteristic of the metal spraying process, and would be produced by any such "line of sight" deposition process.
  • Metal spraying is used because it is one of the few processes capable of applying a superalloy, with all its diverse constituents.
  • Another process that may be used is a physical vapor deposition process, since such process has been shown to be capable of applying MCrAlY coatings and the like. See U.S. Pat. No. 4,153,005 to Norton et al.
  • the blade 14 is subjected to a hot isostatic pressing procedure.
  • this comprises deforming the matrix material 16 beyond its yield or creep-limit point at an elevated temperature.
  • the part is subjected to argon pressure while at elevated temperature, to close the aforementioned pores and voids, and to enhance the bond between the matrix 16, particles 18, and blade tip 11.
  • a temperature of about 1,100° C. and a gas pressure of about 138 MPa applied for two hours is sufficient.
  • Other hot pressing procedures may be used to consolidate the matrix material 16 and achieve the object of densification and bonding.
  • the rough surface of the abrasive layer 10, as shown in FIG. 9, is machined using a conventional procedure such as grinding to produce a smooth, planar suface, as shown in FIG. 10.
  • the thickness of abrasive particles 18 and matrix material 16 is T.
  • the surface of the abrasive layer 10 is contacted with an etchant or other substance which will attack and remove some of the matrix material 16, causing the particles 18 to project into space.
  • electrochemical machining can be used, as is described in U.S. Pat. No. 4,522,692 to Joslin. This step reduces the matrix thickness to a dimension W, which is about 50-90 percent of the dimension T, and results in the shape schematically shown in Fig. 3.
  • FIGS. 4-8 show the preferred embodiment of the invention, i.e., the use of a perforated plate 42 to deposit the particles 18 on the blade tip 11, the apertures in the transfer tool may be defined by other means.
  • One arrangement within the scope of the invention are hollow cylinders such as tubes or needles, which are spaced apart relative to each other such that the apertures (the cylinder ends) are arranged in the same pattern as the perforations in the plate. When a vacuum is drawn through the cylinders, only one particle will overlie each cylinder end. The particles are dropped from the cylinders in the same manner as they are dropped from the plate, as described above.
  • the aspect ratio of the particles is less than about 1.9 to 1 and preferably is about 1.5 to 1 or less.
  • the aspect ratio is defined herein as the average ratio of the longest particle dimension to the cross sectional dimension, as such is measured on a Quantimet Surface Analyzer (Cambridge Instruments, Cambridge, England).
  • the present invention is especially useful in providing a more effective abrasive layer (after the matrix is partially chemically milled away) compared to abrasive layers of the prior art.
  • abrasive layers having the same volume percent of identically sized and shaped particles are made, first using the invention technique and second, using the prior art powder metal technique, as represented in FIG. 2.
  • the area of abrasive particulate exposed at the surface of the invention and prior art layers, after the grinding operation, will be approximately the same. But the particulate deposited according to the invention will be distributed considerably more uniformly.
  • abrasive particles are placed in a uniform distribution on the blade tip, applications are contemplated in which there need be a greater or lesser concentration of particles at one or another portion of the tip. To achieve such a distribution of particles, the pattern of perforations in the plate is modified accordingly.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Manufacturing Of Printed Wiring (AREA)
  • Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
US06/842,591 1986-03-21 1986-03-21 Method for depositing a layer of abrasive material on a substrate Expired - Lifetime US4680199A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US06/842,591 US4680199A (en) 1986-03-21 1986-03-21 Method for depositing a layer of abrasive material on a substrate
EP87630036A EP0238434A3 (en) 1986-03-21 1987-03-19 Method for depositing a layer of abrasive material on a substrate
AU70411/87A AU585800B2 (en) 1986-03-21 1987-03-19 Method for depositing a layer of abrasive material on a substrate
MX005642A MX166013B (es) 1986-03-21 1987-03-20 Metodo para depositar una capa de material abrasivo sobre un substrato
JP62067762A JPS62246466A (ja) 1986-03-21 1987-03-20 物品の表面上に単層の粒子を配置する方法
CA000532636A CA1302798C (en) 1986-03-21 1987-03-20 Method for depositing a layer of abrasive material on a substrate
IL81948A IL81948A (en) 1986-03-21 1987-03-20 Method for depositing a layer of abrasive material on a substrate
KR1019870002588A KR950006398B1 (ko) 1986-03-21 1987-03-21 블레이드팁 표면에 단일입자층을 부착하기 위한 방법

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/842,591 US4680199A (en) 1986-03-21 1986-03-21 Method for depositing a layer of abrasive material on a substrate

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US4680199A true US4680199A (en) 1987-07-14

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US06/842,591 Expired - Lifetime US4680199A (en) 1986-03-21 1986-03-21 Method for depositing a layer of abrasive material on a substrate

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US (1) US4680199A (es)
EP (1) EP0238434A3 (es)
JP (1) JPS62246466A (es)
KR (1) KR950006398B1 (es)
AU (1) AU585800B2 (es)
CA (1) CA1302798C (es)
IL (1) IL81948A (es)
MX (1) MX166013B (es)

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WO1994027833A1 (en) * 1993-05-25 1994-12-08 Ultimate Abrasive Systems, Inc. Patterned abrasive material and method
US5441764A (en) * 1991-02-08 1995-08-15 Sandvik Ab Method of manufacturing a compound body and the resulting body
EP0732175A1 (en) * 1989-01-30 1996-09-18 DeKOK, Peter T. Abrasive tool and method for making
US5620489A (en) * 1994-04-08 1997-04-15 Ultimate Abrasive Systems, L.L.C. Method for making powder preform and abrasive articles made thereform
US5817204A (en) * 1991-06-10 1998-10-06 Ultimate Abrasive Systems, L.L.C. Method for making patterned abrasive material
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US6355086B2 (en) 1997-08-12 2002-03-12 Rolls-Royce Corporation Method and apparatus for making components by direct laser processing
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US6669745B2 (en) 2001-02-21 2003-12-30 3M Innovative Properties Company Abrasive article with optimally oriented abrasive particles and method of making the same
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US6793968B1 (en) * 1999-03-04 2004-09-21 Siemens Aktiengesellschaft Method and device for coating a product
US20040194689A1 (en) * 1997-04-04 2004-10-07 Chien-Min Sung High pressure superabrasive particle synthesis
US6884155B2 (en) 1999-11-22 2005-04-26 Kinik Diamond grid CMP pad dresser
US20050136667A1 (en) * 1997-04-04 2005-06-23 Chien-Min Sung Superabrasive particle synthesis with controlled placement of crystalline seeds
US20050241239A1 (en) * 2004-04-30 2005-11-03 Chien-Min Sung Abrasive composite tools having compositional gradients and associated methods
US20060016127A1 (en) * 1997-04-04 2006-01-26 Chien-Min Sung Superabrasive particle synthesis with controlled placement of crystalline seeds
US20060073774A1 (en) * 2004-09-29 2006-04-06 Chien-Min Sung CMP pad dresser with oriented particles and associated methods
US7089925B1 (en) 2004-08-18 2006-08-15 Kinik Company Reciprocating wire saw for cutting hard materials
US20060222776A1 (en) * 2005-03-29 2006-10-05 Honeywell International, Inc. Environment-resistant platinum aluminide coatings, and methods of applying the same onto turbine components
US7140952B1 (en) 2005-09-22 2006-11-28 Pratt & Whitney Canada Corp. Oxidation protected blade and method of manufacturing
US7201645B2 (en) 1999-11-22 2007-04-10 Chien-Min Sung Contoured CMP pad dresser and associated methods
US20080038575A1 (en) * 2004-12-14 2008-02-14 Honeywell International, Inc. Method for applying environmental-resistant mcraly coatings on gas turbine components
US20090053422A1 (en) * 2007-08-24 2009-02-26 Strock Christopher W Masking fixture for a coating process
US20090257942A1 (en) * 2008-04-14 2009-10-15 Chien-Min Sung Device and method for growing diamond in a liquid phase
US20100024968A1 (en) * 2008-07-30 2010-02-04 United Technologies Corporation Adhesive installation tool
US20100288563A1 (en) * 2009-05-14 2010-11-18 Smith Redd H Methods of use of particulate materials in conjunction with braze alloys and resulting structures
CN101653928B (zh) * 2008-08-19 2011-08-03 苏新页 金刚石有序分布黏性转移方法和黏性转移带
US20120193854A1 (en) * 2010-07-23 2012-08-02 Hilti Aktiengesellschaft Device for positioning cutting particles
US8393934B2 (en) 2006-11-16 2013-03-12 Chien-Min Sung CMP pad dressers with hybridized abrasive surface and related methods
US8398466B2 (en) 2006-11-16 2013-03-19 Chien-Min Sung CMP pad conditioners with mosaic abrasive segments and associated methods
US8556579B2 (en) 2009-05-21 2013-10-15 Rolls-Royce Plc Composite aerofoil blade with wear-resistant tip
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EP0238434A2 (en) 1987-09-23
KR950006398B1 (ko) 1995-06-14
CA1302798C (en) 1992-06-09
AU7041187A (en) 1987-09-24
JPS62246466A (ja) 1987-10-27
IL81948A (en) 1989-12-15
IL81948A0 (en) 1987-10-20
EP0238434A3 (en) 1989-09-13
AU585800B2 (en) 1989-06-22
MX166013B (es) 1992-12-16
KR870009107A (ko) 1987-10-23

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